67-06-02 BRITISH AIRCRAFT: Amdt. 39-359 Part 39 Federal Register March 1, 1967. Applies to Model BAC 1-11 200 and 400 Series Airplanes.
Compliance required as indicated.
To prevent the inflight loss of engine stub access panels, accomplish the following:
(a) Within the next 150 hours' time in service after the effective date of this AD, accomplish the following:
(1) Inspect the access panels Camloc fasteners and sliding bar type fasteners to ensure they are locked in accordance with British Aircraft Corporation One-Eleven Alert Service Bulletin No. 54-A-PM-2649, dated September 22, 1966, or later ARB-approved issue.
(2) Inspect the access panels for vertical movement. If found in excess of 0.1 inch, replace the Camloc grommets with steel grommets P/N 4002-0 or an FAA-approved equivalent.
(b) Within the next 600 hours' time in service after the effective date of this AD, accomplish the following:
(1) Inspect to ensure that each of the clearances betweenthe leading and trailing edges of L.H. panels F3-3 and F3-4 and R.H. panels F3-24 and F3-25 is not greater than 0.080 inch. If any clearance is found to be greater, remove and reposition the two spigots P/N AB 16-549 to the forward face of the channel section and open up and countersink the existing rivet holes to receive 5/32 inch diameter 100 degree rivets to material Specification L86, or FAA- approved equivalent, to attach the spigots.
(2) Inspect to ensure that a continuous line has been stenciled across the sliding bar fastener boss and skin in accordance with British Aircraft Corporation One-Eleven Alert Service Bulletin No. 54-A-PM-2649, dated September 22, 1966, or later ARB-approved issue. If this has not been accomplished, aline the locked indicator marks on the sliding bar fastener boss and the skin and stencil, with paint of a contrasting color to the local finish, a continuous line across the boss and the skin in line with the existing locked indicator marks.(3) Operate the sliding bar fasteners to ensure that the snapover locking action is positive and that no looseness exists. Lubricate and operate several times, in accordance with British Aircraft Corporation One-Eleven Alert Service Bulletin No. 54-A-PM-2649, dated September 22, 1966, or later ARB-approved issue, any fastener that fails to meet this requirement. Replace any fastener that fails to respond to this treatment with a new part.
(4) Replace Camloc fastener grommets with steel grommets P/N 4002-0 or an FAA-approved equivalent.
(c) Within the next 1,800 hours' time in service after the effective date of this AD, remove the access panels and re-lubricate the sliding bar fasteners using grease to Process Specification VP 93/2, or an FAA-approved equivalent.
(d) The requirements of this AD do not apply to those airplanes that have been modified in accordance with British Aircraft Corporation One-Eleven Alert Service Bulletin No. 54-A-PM-2649, dated September 22, 1966, or later ARB-approved issue.
This directive effective March 6, 1967.